ONERA OA206 AIRFOIL (oa206-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA206 AIRFOIL (oa206-il) Reynolds number: 50,000 Max Cl/Cd: 27.13 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa206-il-50000-n5.txt Download as CSV file: xf-oa206-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA OA206 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6757 0.12811 0.12146 0.0373 1.0000 0.0957
-9.500 -0.6813 0.12503 0.11845 0.0328 1.0000 0.0993
-9.250 -0.6910 0.12206 0.11558 0.0267 1.0000 0.1003
-9.000 -0.6742 0.11611 0.10962 0.0298 1.0000 0.1029
-8.750 -0.6664 0.11198 0.10549 0.0296 1.0000 0.1064
-8.500 -0.6659 0.10813 0.10169 0.0269 1.0000 0.1107
-8.250 -0.6838 0.10470 0.09836 0.0159 1.0000 0.1143
-8.000 -0.6686 0.09951 0.09320 0.0196 1.0000 0.1172
-7.500 -0.6703 0.09109 0.08474 0.0083 1.0000 0.1290
-7.000 -0.6508 0.08223 0.07590 0.0081 1.0000 0.1451
-6.750 -0.6252 0.07225 0.06543 -0.0009 1.0000 0.0694
-6.500 -0.6097 0.06635 0.05895 -0.0053 1.0000 0.0581
-6.250 -0.5948 0.06174 0.05424 -0.0061 1.0000 0.0573
-6.000 -0.5786 0.05733 0.04966 -0.0069 1.0000 0.0560
-5.750 -0.5604 0.05302 0.04509 -0.0077 1.0000 0.0539
-5.500 -0.5400 0.04881 0.04052 -0.0085 1.0000 0.0520
-5.250 -0.5176 0.04479 0.03598 -0.0091 1.0000 0.0503
-5.000 -0.4934 0.04109 0.03176 -0.0094 1.0000 0.0492
-4.750 -0.4680 0.03779 0.02794 -0.0095 1.0000 0.0486
-4.500 -0.4423 0.03506 0.02479 -0.0095 1.0000 0.0500
-4.250 -0.4158 0.03274 0.02205 -0.0094 1.0000 0.0534
-4.000 -0.3880 0.03045 0.01928 -0.0091 1.0000 0.0554
-3.750 -0.3598 0.02829 0.01666 -0.0087 1.0000 0.0563
-3.500 -0.3314 0.02644 0.01444 -0.0082 1.0000 0.0577
-3.250 -0.3043 0.02460 0.01249 -0.0077 1.0000 0.0608
-3.000 -0.2775 0.02330 0.01112 -0.0072 1.0000 0.0682
-2.750 -0.2500 0.02208 0.00969 -0.0064 1.0000 0.0730
-2.500 -0.2243 0.02084 0.00837 -0.0058 1.0000 0.0792
-2.250 -0.1990 0.01985 0.00733 -0.0053 1.0000 0.0931
-2.000 -0.1738 0.01886 0.00632 -0.0048 1.0000 0.1132
-1.750 -0.1068 0.01481 0.00557 -0.0084 1.0000 1.0000
-1.500 -0.0841 0.01469 0.00506 -0.0077 1.0000 1.0000
-1.250 -0.0619 0.01459 0.00471 -0.0069 1.0000 1.0000
-1.000 -0.0403 0.01451 0.00443 -0.0061 1.0000 1.0000
-0.750 -0.0193 0.01446 0.00422 -0.0052 1.0000 1.0000
-0.500 0.0010 0.01444 0.00407 -0.0041 1.0000 1.0000
-0.250 0.0208 0.01444 0.00395 -0.0030 1.0000 1.0000
0.000 0.0401 0.01446 0.00390 -0.0018 1.0000 1.0000
0.250 0.0590 0.01451 0.00389 -0.0005 1.0000 1.0000
0.500 0.0780 0.01459 0.00393 0.0007 1.0000 1.0000
0.750 0.0974 0.01469 0.00402 0.0017 1.0000 1.0000
1.000 0.1172 0.01483 0.00416 0.0026 1.0000 1.0000
1.250 0.1375 0.01500 0.00435 0.0034 1.0000 1.0000
1.500 0.1627 0.01522 0.00462 0.0031 0.9968 1.0000
1.750 0.2184 0.01551 0.00503 -0.0028 0.9755 1.0000
2.000 0.2716 0.01576 0.00548 -0.0079 0.9488 1.0000
2.250 0.3137 0.01595 0.00584 -0.0103 0.9141 1.0000
2.500 0.3453 0.01606 0.00611 -0.0102 0.8718 1.0000
2.750 0.3713 0.01611 0.00632 -0.0086 0.8222 1.0000
3.000 0.3940 0.01616 0.00641 -0.0062 0.7639 1.0000
3.250 0.4148 0.01628 0.00646 -0.0032 0.6938 1.0000
3.500 0.4350 0.01658 0.00654 -0.0003 0.6121 1.0000
3.750 0.4558 0.01711 0.00676 0.0019 0.5304 1.0000
4.000 0.4781 0.01783 0.00723 0.0034 0.4610 1.0000
4.250 0.5016 0.01862 0.00782 0.0043 0.4046 1.0000
4.500 0.5256 0.01947 0.00853 0.0049 0.3563 1.0000
4.750 0.5501 0.02032 0.00934 0.0054 0.3088 1.0000
5.000 0.5744 0.02117 0.01013 0.0057 0.2569 1.0000
5.250 0.5987 0.02208 0.01096 0.0058 0.1938 1.0000
5.500 0.6226 0.02342 0.01206 0.0058 0.1348 1.0000
5.750 0.6464 0.02510 0.01358 0.0061 0.0948 1.0000
6.000 0.6701 0.02693 0.01539 0.0067 0.0772 1.0000
6.250 0.6939 0.02863 0.01721 0.0071 0.0641 1.0000
6.500 0.7182 0.03069 0.01963 0.0078 0.0574 1.0000
6.750 0.7411 0.03303 0.02208 0.0083 0.0527 1.0000
7.000 0.7646 0.03550 0.02509 0.0088 0.0472 1.0000
7.250 0.7861 0.03815 0.02807 0.0091 0.0439 1.0000
7.500 0.8055 0.04146 0.03170 0.0093 0.0423 1.0000
7.750 0.8222 0.04561 0.03634 0.0095 0.0414 1.0000
8.000 0.8350 0.05023 0.04163 0.0093 0.0408 1.0000
8.250 0.8423 0.05534 0.04735 0.0087 0.0402 1.0000
8.500 0.8438 0.06083 0.05335 0.0075 0.0396 1.0000
8.750 0.8400 0.06658 0.05947 0.0055 0.0394 1.0000
9.000 0.8317 0.07252 0.06564 0.0026 0.0395 1.0000
9.250 0.8201 0.07847 0.07172 -0.0010 0.0398 1.0000
9.500 0.8085 0.08499 0.07827 -0.0060 0.0402 1.0000
9.750 0.8009 0.09236 0.08563 -0.0120 0.0407 1.0000
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Polar data table (+)
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